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ERJ > EMB 175 QUICK LIMITATION and other numbers > Flashcards

EMB 175 QUICK LIMITATION and other numbers Flashcards

1
Q

Weights LR/LL

A

MRW 85,870 / 85,450
MTOW 85,517 / 85,098
MLW 74,957 / 74,957
MZFW 69,886 / 69,467

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2
Q

MIN FLIGHT CREW

A

2 = pilot and copilot

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3
Q

max runway slope

A

+/- 2%

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4
Q

runway surface type

A

paved

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5
Q

max altitude for flaps extended

A

20,000

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6
Q

max operating altitude

A

41,000*

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7
Q

max T&O & landing altitude

A

10,000

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8
Q

min T&O & landing altitude

A

-1,000

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9
Q

Max speed to open direct vision window

A

160

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10
Q

max latitude for stationary alignment

A

78.25 North and South

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11
Q

min ambient temp approved for T&O

A

-54

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12
Q

max ambient air temp for takeoff and landing

A

52C

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13
Q

VLO RET, VLO EXT, VLE speeds (gear)

A

250

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14
Q

Flap speeds

A

flap 1 230
flap 2 215
flap 3 200
flap 4 & 5 180
flap Full 165

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15
Q

aircraft max operating speed

A

VMO/MMO

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16
Q

max operating mach

A

.82

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17
Q

max airspeed for RAT operation

A

VMO/MMO

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18
Q

turbulent air below 10,000

A

250

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19
Q

turbulent air above 10,000

A

270/.76 whichever is lower

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20
Q

max tire limit ground speed

A

195

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21
Q

max windshield wiper speed

A

253

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22
Q

max operating speed up to 8,000
8,000 - 10,000
10,000 - FL290
FL290-FL410

A

300

300-320
320
.82

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23
Q

Max recommended xwind for landing

A

Dry 38
wet 31
compacted snow 20
standing water/slush/wet snow/dry snow 18
ice 12

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24
Q

max static takeoff crosswind

A

28 knots

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25
Q

cargo loading weights

A

FWD 3306
AFT 2535

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26
Q

icing conditions may exist

A

icing conditions may exist whenever the Outside Air Temperature (OAT) on the
ground or for Takeoff, or Total Air Temperature (TAT) in-flight, is 10°C or below
and visible moisture in any form is present (such as clouds, fog with visibility of
one mile or less, rain, snow, sleet and ice crystals)

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27
Q

APU min start temp (outside temp)

A

-54C

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28
Q

APU max alt to start

A

30,000

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29
Q

APU max operating alt

A

33,000

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30
Q

APU max electrical generation

A

33,000

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31
Q

APU bleed altitude

A

15,000

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32
Q

altitude for APU to assist engine start

A

21,000

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33
Q

APU max rotor speed %

A

108%

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34
Q

APU amber range (no time limit)

A

662 - 717C

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35
Q

APU EGT start temp

A

1032

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36
Q

APU EGT continuous TEMP

A

717

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37
Q

APU start limits times

A

1 & 2 1 min on/1 min off

3 1 min on/5 mins off

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38
Q

CAT II flaps position

A

flaps 5

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39
Q

CAT II demonstrated wind components (not considered limiting)

A

headwind 25
tailwind 10
crosswind 12

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40
Q

CAT II required equipment

A

2 Air Data System (ADS).
2 Flight Director Systems.
2 Inertial Reference Systems.
2 Primary Flight Displays (PFD).
2 VOR/ILS NAV System.
Autopilot System Channel.
Cat II Engagement Logic.
EGPWS.
Radio Altimeter.
Rudder in Normal Mode.
SPOILER FAULT message not presented.
VHF/COMM System.
Windshield Wipers.

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41
Q

max fuel capacity total

A

20,935

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42
Q

max fuel capacity per tank

A

10,392.5

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43
Q

unusable fuel per tank

A

75 lbs

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44
Q

min fuel tank temp

A

-37C in left tank

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45
Q

max fuel imbalance

A

794

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46
Q

max differential pressure

A

8.4 psi

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47
Q

Maximum differential overpressure

A

8.8

48
Q

Maximum differential negative pressure

A

-.5

49
Q

Maximum differential pressure for Takeoff and Landing

A

.2

50
Q

Single PACK operations limit

A

FL310

51
Q

Thrust reversers conditions

A

Upon Landing, if thrust reversers have been used, reverser should be set to MIN REV at 60 KIAS, and be closed by 30 KIAS.
A Go-Around Maneuver should not be attempted after Thrust Reversers have been deployed

52
Q

autopilot use

A

min engagement height in AFM - 400
min engagement height in CFM - 1,000’*
min use height - 50’

53
Q

CF 34-8E5 engines with takeoff thrust time limited to ____ minutes OR POSTMOD SB170-73-0002

A

10 minutes

54
Q

N1 max percentage

A

99.5%

55
Q

N2 min - max percentage

A

58.5% - 99.4%

56
Q

ITT max Start

A

815

57
Q

ITT max take off and go around temp and time limits

A

990C

  1. Time limited to 5 min with all engines operative. This limit is extended to 10 min with one engine inoperative for airplanes Post- Mod SB 170-73-0002 or equipped with an equivalent modification factory incorporated.
  2. Can be exceeded up to 1006°C during the first 2 minutes.
58
Q

ITT max continuous temp

A

960

59
Q

oil pressure PSI min- max

A

25-95psi

60
Q

oil temp continuous temp

A

155

61
Q

oil temp transient temp

A

163 (Transient operation above 155°C limited to 15 minutes.)

62
Q

engine starter limits attempts

A

1 and 2 - 90 Seconds on/ 10 Seconds off
3 through to 5 - 90 Seconds On/5 Minutes off

120 seconds on In-flight

63
Q

engine dry motor starter limits attempts

A

1 - 90 Seconds on/ 5 Minutes off
2 through 5 - 30 Seconds on/5 Minutes off

After five sequential motorings, cycle may be repeated following a 15 minute cool down period.

64
Q

for FLEX - The total thrust reduction must not exceed ____ of the full Takeoff thrust.

A

25%

65
Q

FLEX is prohibited on ____ runways

A

contaminated

66
Q

TAS, TAT and SAT information are only valid above____ KIAS

A

60

67
Q

While transmitting in ____ the standby magnetic compass indication is not valid.

A

VHF1

68
Q

Baro altimeter minimums must be used for all ____Approaches.

A

CAT I

69
Q

Pilots are authorized to deviate from their current Air Traffic Control (ATC) clearance to the extent necessary to comply with an _____

A

EGPWS warning.

70
Q

Localiser Back course Approaches using _____ are prohibited.

A

IESS

71
Q

RSVM required equipment list

A

(2) Air Data Computers (ADC) (Two must be operational)
(2) Altitude Reporting Transponders (One must be operational)
(1) Altitude Alerting System (Must be operational)
(1) Autopilot (Must be operational)

72
Q

RVSM tolerances

A

Total Vertical Error +/- 300 ft.

Altimetry System Error +/- 245 ft.

Assigned Altitude Deviation +/- 300 ft.

73
Q

use of Temperature compensation

A

The use of temperature compensation feature must be coordinated with ATC if Baro-VNAV operation is intended.

The use of temperature compensation feature is required if Baro-VNAV operation outside the temperature limits published on Approach
procedure chart is intended.

74
Q

Kinds of Airplane Operation

A
  1. VFR and IFR.
  2. Icing Conditions.
  3. Category I and II.
  4. Extended Overwater Operation.
  5. RVSM.
  6. RNP.
75
Q

APU max start temp (outside temp)

A

52C

76
Q

In the event of a Landing below ___, the airplane may not Takeoff without further maintenance inspection.

A

-40C

77
Q

Flaps load factor

A

Flaps Up -1.00g to 2.5 g

Flaps Down 0g to 2 .00g

78
Q

Fuel Specification

A

JP8

79
Q

Crossfeed Operation

A

Crossfeed Selector Knob must be set OFF during Takeoff and Landing

80
Q

The maximum N1 percentage with brakes applied is

A

60%

81
Q

For Flex - reduction must not exceed

A

The total thrust reduction must not exceed 25% of the full Takeoff thrust.

82
Q

flex is prohibited on

A

Use of reduced Takeoff thrust procedures is not allowed on runways contaminated with standing water, slush, snow or ice and are not allowed on wet runways
unless suitable performance accountability is made for the increased stopping distance on the wet surface.

83
Q

The TO DATASET MENU on the MCDU must be set to ENG in the following cases when OAT is

A

between 5°C and 10°C and:
1. If there is any possibility of encountering visible moisture up to 1,700 ft AFE, or
2. When operating on ramps, taxiways or runways where surface snow, ice, standing water or slush may be ingested by the engines or freeze on engines, nacelles or engine sensor probes.

84
Q

The TO DATASET MENU on the MCDU must be set to ALL in the following cases when

A

OAT is below 5°C and:
1. If there is any possibility of encountering visible moisture up to 1,700 ft AFE, or
2. When operating on ramps, taxiways or runways where surface snow, ice, standing water or slush may be ingested by the engines or freeze on engines, nacelles or engine sensor probes.

85
Q

Steering degrees for steering handle and rudder

A

O - 10kts 76 degrees
11 - 26kts 20 degrees
27 - 100kts 7 degrees (rudder)

86
Q

TOGA pitch bar range in degrees

A

8 - 18 degrees

87
Q

Fuel low level warning occurs in each tank at what lbs?

A

660lbs

88
Q

turn radius for 180 degrees

A

59’ 2”

89
Q

aircraft dimensions

A

height 32’ 4”
wing span 93’ 11”
length 103’ 11”

90
Q

IESS alignment time

A

90 seconds

91
Q

GE CF34-8E5 max thrust

A

13,000 - 14,200

92
Q

hydraulic temp limits

A

100C HYD HI TEMP EICAS
125C auto shutoff
145C HYD OVERHEAT EICAS

93
Q

Taxi speeds

A

straight/Dry 30
Turns/dry 10
straight/wet or contaminated 10
turns/wet or contaminated 5

94
Q

two engine out speed

A

pitch for 250kts MINIMUM

95
Q

single engine drift down speed

A

green dot

96
Q

green dot represents

A

1.3G over stick shaker speed

97
Q

Pitch angles for flap positions

A

Flaps 1 11 degrees
Flaps 2 10 degrees
Flaps 4 12 degrees

98
Q

radar altimeter comes alive at

A

2,500 AGL

99
Q

percent of recirculation air

A

52% fresh
48% recirculated

100
Q

The APU oil capacity is

A

4.12 qt

101
Q

BATT 1 (2) OVERTEMP EICAS message will appear at what temp?

A

70C for 2 seconds

102
Q

Manuals and Documents (15 items)

A
  1. Jumpseat Briefing Card.
  2. Passenger Briefing Safety Information Cards.
  3. Passenger Count Card.
  4. TOLD Cards.
  5. 2 CAT II INFORMATION and CALLOUTS Cards.
  6. 2 ECS Off Takeoff checklist, Engine Battery Start checklists.
  7. 2 EPCs.
  8. 2 Icing Conditions, Cold Weather and Cold Soak Operations.
  9. 2 Lightning Strike, Turbulent Air Penetration, Hot Weather.
  10. 2 Normal Operations Checklist(s).
  11. Airworthiness Certificate and Registration.
  12. AML
  13. QRH
  14. Radio Station Certificate.
  15. W&B Manifest.
103
Q

Abnormal Engine Start Indications

A

No positive oil pressure indication within 10 seconds after N2 Speed starts to increase.

During engine start with tailwind, if a positive increase of N1 is not indicated before starter cutout (50% N2). In this case, the airplane should be repositioned prior to engine start to minimize tailwind effects

If ITT does not rise within 30 seconds after fuel is applied.

ITT exceeds start limit (Hot Start).

If oil pressure stabilizes below the engine limits.

N1 and/or N2 failing to accelerate to stable idle Speed (Hung Start).

An intermittent electrical pneumatic or starter malfunction occurs before the starter disengagement

104
Q

E-175 aircraft are Group ___ aircraft and require a minimum _____ ft of runway at
Sea Level.

A

7
6,000

105
Q

takeoff briefing items (15)

A

right/left seat t/o

flex, T.O 1,2, Flaps 1,2,4 (point to TOLD CARD)

departing on runway (point to TOLD CARD)

TO SID & TRANSITION (point to TOLD CARD)

cleared to ALT (point at ALT window)

we are using FMS speeds (point to speed window verify magenta FMS speeds)

LNAV is Armed or HDG at 400” (point to LNAV armed in FMA or to the HDG button)

Our climb Seq VNAV or FLCH (point to the VNAV or FLCH button)

Emer return to what airport (we could have a TO ALT to consider)

Our SE Dep Procedure is (point at TOLD CARD)

Min flap retract alt is (point to TOLD CARD)

EPC/QRH Cntr Aft Pedstal (reaching back pointing at them with left hand and looking at them)

WX, specials, MELs, (specials Anti-ice, wet/contaminated runway, ECS-OFF etc.)

Taxi to Rnwy?? via ?? and we will HOLD SHORT

we have/dont have any Hot Spots or Incursion Spots

106
Q

emergency equipment (7)

A

CEFFLOP

Crash Axe (1)
Escape Ropes (2)
Fire Extinguisher (1)
Flashlights (2)
Life Vests (3)
Oxygen Masks (3)
PBE (1)

107
Q

Flight Kit items (12)

A

Airman Certificate

Extra Pair of Corrective Lenses* Only required if wearing corrective lenses

FCC Restricted Radio
Telephone Operating Permit

Flashlight

Jeppesen Inflight Pubs (EFB or Paper)

Log book

Medical Certificate

Mesa Airlines, Inc. ID Card

Passport

Pen

Required Manuals (EFB or Paper)

Training Folder Only required if in training

108
Q

considered stable approach

A

Stabilized Approach Criteria
1. Flights will be stabilized by 1,000 feet AFE.
2. An approach is considered to be stable when all of the following conditions are met:
a. All appropriate briefings and checklists have been accomplished.
b. The aircraft is in the planned landing configuration.
NOTE
The planned landing configuration is gear down and locked, final landing flaps, and flight spoilers are retracted.
c. The aircraft is on the correct track.
NOTE
The correct track includes normal maneuvering required to align with the final approach course. In VMC conditions this may include turns below 1,000 feet (AFE) but must be aligned by 500 feet (AFE). However, all of the criteria for stabilized approach must be met by 1,000 feet (AFE).
d. The aircraft is not more than the planned approach speed +10 KIAS, while correcting to the proper speed, and not less than VREF.
NOTE
Adjustments may be made for ground speed when applicable. Momentary excursions (deviations which last only a few seconds with every indication that it will return to a stabilized criteria) are acceptable.
e. The power setting is appropriate for the aircraft configuration.
NOTE
At no point except for rollout and flare should the thrust levers be reduced to idle below 1,000 feet AGL. If this occurs then a goaround is mandatory.
f. The rate of descent is no greater than 1,000 fpm.
NOTE
If an expected rate of descent greater than 1,000 fpm. is planned, a special approach briefing should be performed.
NOTE
If an unexpected sustained rate of descent greater than 1,000 fpm. is encountered during the approach, a missed approach or goaround should be performed.

g. After glidepath intercept, or after the FAF, the pilot flying (PF) requires no more than normal corrections to maintain the correct track and desired profile to landing within the touchdown zone.
NOTE
Normal bracketing corrections relate to bank angle of not more than 30°, rate of descent ±300 fpm. deviation from target, and power management in the range required to maintain a constant rate of descent and speed. Normal bracketing corrections occasionally involve momentary overshoots made necessary by atmospheric conditions. Such overshoots are acceptable. Frequent or sustained overshoots caused by poor pilot technique are not normal bracketing corrections.

109
Q

Internal Safety Inspection Flow Items

A

Manuals and Documents
Check that the following hard copy manuals, checklists, charts and certificates are onboard and current:
l. Jumpseat Briefing Card.
b. Passenger Briefing Safety Information Cards.
n. E-175 Passenger Count Card.
d. TOLD Cards.
k. Two CAT II INFORMATION and CALLOUTS Cards.
j. Two ECS Off Takeoff, Engine Battery Start checklists.
c. Two EPCs.
h. Two Icing Conditions, Cold Weather and Cold Soak Operations.
i. Two Lightning Strike, Turbulent Air Penetration, Hot Weather.
g. Two Normal Operations Checklist(s).
a. Quick Reference Handbook.
e. Airworthiness Certificate and Registration.
o. Aircraft Maintenance Log (AML).
f. Radio Station Certificate.
m. W&B Manifest.

EFB Manuals
Check that the following manuals are current on the EFB and are copied
into an approved PDF Reader App:
a. (195) Carry-On Baggage Program.
b. (211) Non-Essential Equipment and Furnishings (NEF List).
c. (251) E-175 Minimum Equipment List (MEL).
d. (252) E-175 Configuration Deviation List (CDL).
e. (330) Hazardous Material Manual.
f. (410) General Operations Manual (GOM).
g. (930) E-JET Company Flight Manual (CFM).
h. (931) E-JET Quick Reference Handbook (QRH).
i. Max Temp Takeoff Chart.
j. (400) Mesa Airlines, Inc. Operations Specifications (Ops Specs).
k. Flight Duty Time Limitations & Rest Requirements.
l. EGPWS.
m. (916) Honeywell FMS (E-JET) (LR).
n. (917) E-JET FMS (LL).

Doorway
a. PBE (1) ……………………………………………….CHECK
b. Halon Fire Extinguisher (1) …………………….CHECK
Pressure in green, pin installed.
c. Crash Axe (1)…………………………………… STOWE

Captain’s Side
a. Flashlight ………………………………. CHECK LED ON
The aircraft flashlights are for emergency use only.
b. Life Vest (1)………………………………. INSTALLED IN
SEAT BACK POCKET
c. Jumpseat Life Vest (1)…………………INSTALLED IN
SEAT BACK POCKET
d. Circuit Breakers ………….CLOSED OR COLLARED
e. Escape Rope ……………………………………….CHECK
f. Headset ………………………………………..INSTALLED

First Officer’s Side
a. Flashlight. ……………………………… CHECK LED ON
The aircraft flashlights are for emergency use only.
b. Circuit Breakers ………….CLOSED OR COLLARED
c. Life Vest (1)……………. …………………INSTALLED IN
SEAT BACK POCKET
d. Escape Rope ……………………………………….CHECK
e. Landing Gear and RAT Safety Pins ……ONBOARD
f. Headset ………………………………………………CHECK

Aft Control Pedestal
a. Observer O2…………………………………………CHECK
b. Observer Audio Panel……………………………….. SET
c. Headset ………………………………………..INSTALLED

Observer Seat
a. Observer Seat………………….. CHECK CONDITION

Maintenance Status

Cockpit Emergency Equipment (CEFFLOP)
a. Protective Breathing Equipment (PBE).
b. Fire Extinguisher.
c. Crash Axe.
d. Life Vests.
e. Escape Ropes.
f. Flashlights

ELECTRIC Panel
a. IDG 1 Selector ………………………………………. AUTO
b. IDG 2 Selector ……………………………………… AUTO
c. GPU Button………………………………. PUSHED OUT
d. AC BUS TIES Selector …………………………… AUTO
e. APU GEN Button ………………………….. PUSHED IN
f. TRU 1 Switch………………………………………… AUTO
g. TRU ESS Switch……………………………………. AUTO
h. TRU 2 Switch………………………………………… AUTO
i. BATT 1 Knob…………………………………………….OFF
j. DC BUS TIES Switch……………………………… AUTO
k. BATT 2 Knob…………………………………………….OFF

FUEL Panel
Verify all fuel pump knobs in AUTO position and XFEED Selector in the
OFF position.

PASSENGER SIGNS Panel
Set the NO SMKG Switch to ON during all flight phases.

Windshield Wipers

HYDRAULIC Panel
a. HYDRAULIC Sys 1 ENG PUMP
SHUTOFF Button ……………………………PUSH OUT
b. PTU Knob …………………………………………….. AUTO
c. HYDRAULIC Sys 2 ENG PUMP
SHUTOFF Button ……………………………PUSH OUT
d. HYDRAULIC System 1, ELEC
PUMP Knob ………………………………………….. AUTO
e. HYDRAULIC System 2, ELEC
PUMP Knob ………………………………………….. AUTO
f. HYDRAULIC System 3, ELEC
PUMP A Knob …………………………………………..OFF
g. HYDRAULIC System 3, ELEC
PUMP B Knob……………………………………….. AUTO

AIR COND/PNEUMATIC Panel
Verify all buttons pushed in.

PASSENGER OXYGEN Panel
Verify Masks Deploy Selector in AUTO.

ELT Switch

LANDING GEAR Lever

ENG 1 & 2 START/STOP Selectors

SPEEDBRAKE Lever

RAT MANUAL DEPLOY Lever

SLAT/FLAP Lever
Verify that the current SLAT/FLAP lever position agrees with the surface
position.

CIRCUIT BREAKERS Panels
Verify both sidewall panels to ensure agreement with maintenance
status.

110
Q

The EMBRAER FBW system is composed of a set of ____ Actuator Control Electronics (ACEs) and ____Flight Control Modules (FCMs):

A

nine ACE
four FCMs

(3)Three Primary-ACEs (P-ACE).
(3) Three Spoiler ACEs (S-ACE).
(2) Two Slat/Flap ACEs (SF-ACE).
(1) One Horizontal Stabilizer ACE (HS-ACE).

(5) Four Flight Control Modules (FCM)

111
Q

Forward Electronic Bay (E-Bay)

A

SPDA 1
Emergency Integrate Control Center (EICC) .
2 P-ACE units
DVDR 1
battery 1
invertor
MAU 1 & 2

112
Q

Center Electronic Bay (E-Bay)

A

Left Integrated Control Center (LICC),
Right Integrated Control Center (RICC) and
SPDA 2.
1 P-ACE units
2 SF-ACE units
MAU 3

113
Q

aft electronics bay

A

HS-ACE
DVDR 2
AICC

114
Q

Pitch trim limits

A

13 up
2 down

115
Q

What are the limits for nosewheel steering?
Angle varies with groundspeed

A

What are the limits for nosewheel steering?
Angle varies with groundspeed

10 knots up to 76 degrees
26 knots up to 20 degrees
over 100 knots maximum 7 degrees

over 76 degrees it goes freewheeling

ERJ (30 decks)

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